N325QS

Part: BATTERY PACK — MALFUNCTIONED (ZONE 200) · airframe 9,445 hrs · 7,361 cycles

CABIN EMERG LIGHT: DURING FLIGHT CONTINUOUS FLASHING OF CABIN EMERGENCY FLOOR AND DOOR EXIT AND CABIN LIGHTS. WITH SWITCHES EITHER IN ARMED OR ON POSITION. VIDEO TO FOLLOW. CORRECTIVE ACTION: REMOVED AND REPLACED #1 AND #2 EMERGENCY BATTERIES IAW EMBRAER PHENOM 300 A.M.M. 33-52-01. REMOVED #1 P/N 640-13595-00 S/N 006343 INSTALLED P/N 640-13595-00 S/N 005711 REMOVED #2 P/N 640-13595-00 S/N 006342 INSTALLED #2 P/N 640-13595-00 S/N 005861.

Part: POWER SUPPLY — FAULTED (EMERGENCY LIGHTS) · airframe 9,125 hrs · 7,089 cycles

EMERGENCY LIGHTS IN THE "ARM" POSITION, EMERGENCY LIGHTS WERE FLASHING AND DRAINED BOTH EMERGENCY BATTERIES. REMOVED AND REPLACED #1 AND #2 EMERGENCY LIGHT POWER UNIT.

Part: LIGHT — BURNED OUT (ZONE 200) · airframe 8,706 hrs · 6,764 cycles

DURING MXC NOTED FWD EXTERIOR EMERGENCY LIGHT RETAINING WATER AND SEVERAL LEDS INOP

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 8,600 hrs · 6,684 cycles

FLOOR EMERG EXIT LIGHT: EMERGENCY FLOOR EXIT LIGHT BELOW SEAT 3 IS OUT OF RECESS AND HANGING IN AISLE BY WIRE. INSERTED AND RESECURED EMERGENCY FIOOR EXIT LIGHT BELOW SEAT 3 SOCKET IAW EMB505 SPM 20·00-00. OPS/CK GOOD, TO CONTINUE

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 8,600 hrs · 6,683 cycles

FLOOR EMERG EXIT LIGHT: FLOOR EMERGENCY EXIT LIGHT BELOW SEAT ONE HAS BEEN PULLED OUT OF ITS RECESS AND IS HANGING IN AISLE BY WIRE. REINSTALLED FLOOR EMERGENCY EXIT LIGHT IN THE FLOOR PATH BELOW SEAT ONE IAW EMB-505 AMM 33-52-11, EMERGENCY LIGHT OPERATIONAL CHECK SATISFACTORY.

Part: BATTERY — NO TEST (ZONE 100) · airframe 8,546 hrs · 6,641 cycles

EMER LIGHTS FLASHING ENROUTE WITH SWITCH IN ARM POSITION. NOW ON STEADY IN ARM POSITION. BEGAN TROUBLESHOOTING, FOLLOWING FIM TASK 33·50·00·810·802-A SETTED EMER LT SWITCH TO THE ARM POSTION, LIGHTS DID NOT FLICKER, LIGHTS CAME ON WITH SWITCH IN ARM POSITION FOR MORE THAN MIN. GAINED ACCESS TO #2 EMER BATTERY, DISCONNECTED CONNECTOR P1360 FROM BATTERY, PLACED SWITCH ON ARM POSTION & LIGHTS DID NOT COME ON. REMOVED AND INSTALLED THE BATTERY IAW AMM 33-52-01. PERFORMED OPS CHECK WITH SAME RESULT, CONTINUED WITH FIM & GAINED ACCESS TO 1# EMER BATTERY. REMOVED #1 AND INSTALLED THE BATTERY IAW AMM 33·52-01, OPS CHECKED GOOD, AIRCRAFT OK TO RETURN TO SERVICE,

Part: UNKNOWN — UNKNOWN (UNKNOWN) · airframe 8,438 hrs · 6,546 cycles

MAIN DOOR: THERE IS A LOOSE SCREW PROTUDING UP ABOUT AN INCH THAT IS CREATING A TRIPPING HAZARD ON THE LEFT CORNER OF THE FIRST STEP ON THE MAIN CABIN ENTRY DOOR. //SIGNOFF// SECURED LOOSE SCREW ON MCD STEP IAW EMB PHENOM 300 MM 52-14-00

Part: WINGLET — CORRODED (ZONE 600) · corrosion level 2 · airframe 8,213 hrs · 6,350 cycles

CORROSION UNDER STATIC WICK BASE ON RH WINGLET TRAILING EDGE CAUSED STATIC WICK BASE TO FALL OFF. CORROSION REMOVAL WAS OUTSIDE OF SRM LIMITS. PERFORMED AN EXTERNAL DOUBLER PATCH AROUND THE TRAILING EDGE (TACO PATCH).

Part: CAM — OVERSERVICED (PAX DOOR) · airframe 7,886 hrs · 6,119 cycles

UPPER LEFT CAM LOCK CLOSED INDICATOR DOESN'T SHOW ANY GREEN THROUGH THE WINDOW. INSPECTED UPPER LEFT CAM LOCK CLOSED INDICATOR, REMOVED STEPS AND CLEANED EXCESS GREASE FROM INDICATOR AND REINSTALLED STEPS, VERIFIED PROPER OPERATION AND INDICATION IAW AMM 52-11-00-200-801.

Part: BATTERY — DEFECTIVE · airframe 6,776 hrs · 5,248 cycles

EMERG LIGHT SWITCH: SWITCH ON THE ARM POSITION DURING FLIGHT ALL EMERGENCY LIGHT CAME ON AND STARTED FLICKERING .PUT SWITCH OFF POSITION BACK TO ARM POSITION AND ALL EMERGENCY LIGHT WERE ON AND FLICKERING AT INTERVAL. // SIGNOFF // REMOVED FAULTY AFT EMERGENCY LIGHTS BATTERY AND REPLACED WITH A NEW CUSTOMER SHIPPED EMERGENCY BATTERY. PERFOR1V1ED A SATISFACTORY OPERATIONAL CHECK OF THE EMERGENCY LIGHT SYSTEM WITH NO DEFECTS NOTED. CLOSED ALL ACCESS GAINED TO FACILITATE THE MAINTENACE, AIRCRAFT INTERIOR RETURN TO ITS ORIGINAL CONFIGURATION. ALL WORK DONE IN REFERENCE WITH EMB-505S AMM 33-52-00.

Part: BALANCE WEIGHT — CORRODED (ZONE 300) · airframe 5,850 hrs · 4,537 cycles

DURING ACCOMPLISHMENT OF EMBRAER SERVICE BULLETIN 505-55-0004 REV 01 (DATED 06/24/2020) WE NOTED THE FOLLOWING MASS BALANCE WEIGHTS BELOW TOLERANCE AT LEFT ELEVATOR: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (13 EACH BELOW MINIMUM OF 84G), HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G), MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-615 AS PER SERVICE BULLETIN INSTRUCTIONS. WE ALSO NOTED THE FOLLOWING RIGHT ELEVATOR MASS BALANCE WEIGHTS BELOW TOLERANCE: ADJUSTABLE WEIGHTS PART NUMBER PE915109-L33 (14 EACH BELOW MINIMUM OF 84G), HORN MASS WEIGHT PART NUMBER PE915109-L42 (1 EACH BELOW MINIMUM OF 1095G), MASS WEIGHT OUTBOARD PART NUMBER PE915109-L41 (1 EACH BELOW MINIMUM OF 2049G). ALL WEIGHTS HAS BEEN REPLACED WITH A NEW MASS WEIGHTS AND THE ELEVATOR BALANCING WAS PERFORMED WITH NO FURTHER DEFECTS NOTED.THE ELEVATOR WAS RE-IDENTIFIED TO PART NUMBER 505-11094-616 AS PER SERVICE BULLETIN INSTRUCTIONS. THIS REPORT COMPLIES WITH FAA 14 CFR PART 135 OPERATOR’S GMM REQUIREMENTS.

Part: HANDLE — BROKEN (PAX DOOR) · airframe 5,616 hrs · 4,371 cycles

PASSENGER DOOR HANDLE BROKE OFF WHILST OPENING THE DOOR. SIGN OFF. REMOVED AND REPLACED MED EXTERNAL DOOR HANDLE. OPS CHECKS GOOD, IAW PH300 MM 52-11-24.

Part: BALANCE WEIGHT — CORRODED (RUDDER) · airframe 5,071 hrs · 3,953 cycles

UPPER RUDDER FIXED MASS BALANCE WEIGHT AND FOUND CORROSION. RUDDER ADJUSTABLE BALANCE WEIGHTS AND FOUND THEM TO HAVE CORROSION

Part: BALANCE WEIGHT — CORRODED (LT ELEVATOR) · airframe 5,071 hrs · 3,953 cycles

CORROSION ON 1 EA RH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS PN#PE915109-L33: CORROSION ON 1 EA LH ELEVATOR ADJUSTABLE MASS BALANCE WEIGHTS PN#PE915109-L33

Part: CONTROLLER — DEFECTIVE (TEMP) · airframe 5,023 hrs · 3,918 cycles

TEMP CONTROL BOTH MODES INOP - AT FL410 DUCT 1 OVERTEMP CAS ILLUMINATED. FOLLOWED THE QRH PROCEDURE. IT DID NOT EXTINGUISH. WE WERE AT THE QRH STEP TO TURN BLEED 1 SWITCH OFF WHEN DUCT 2 OVERTEMP CAS ILLUMINATED. WE CHANGED GEARS AND BEGAN THE DUAL DUCT OVERTEMPRATURE QRH. THE QRH PROCEDURE WAS FOLLOWED TO THE END. WE DIVERTED TO IAD AND LANDED.// SIGNOFF// IREMOVED AND REPLACED TEMPERATURE CONTROLLER, OPS CHECKS GOOD .. WORK DONE IAW EMB-1505 AMM 21-61-01. REMOVED AND REPLACED RAM AIR VALVE ASSEMBLY, OPS CHECKS GOOD REF IEMB505 AMM 21-23-03. REPLACED GROUND COOLING FAN JAW EMB505 MM CH 21-23-05.DURING OPSTHECK FAN DID NOT OPERATE.C/W FIM TASK 21-23-00-810-802-A. AND FOUND NO POWER OR GND ON CONNECTOR P0959. VERIFIED POWER AT CB 0345 ON RPDU AND HAD 28V. CYCLED CB AND !RECONNECTED CONNECTOR P0959 AND CONNECTOR P149L AND PERFORMED OPERATLON CHECK AGAIN OPS CHECKS GOOD.

Part: BRAKE SYS — WEAK (MLG) · airframe 10,442 hrs · 8,600 cycles

BRAKES SPONGY BOTH PEDALS, BOTH SIDES. BLEED LT AND RT BRAKE SYS IAW MM 32-40-00. OPS CHECKED SATISFACTORY.

Part: STARTER GEN — FAULTY (LT ENGINE) · airframe 9,378 hrs · 7,731 cycles

LT FUEL FLOW FLUCTUATION DURING CLIMB AND CRUISE FOLLOWED BY LT GEN FAILURE, FOLLOWED BY LT ENGINE VIBRATION SUB: FOUND LT START GEN EXHAUST DUCT HAS LARGE AMOUNT OF SOOT. REMOVED AND REPLACED LT START GEN. C/W SATISFACTORY, OPS CHECK AND PARALLEL IAW MM 24-10-00.

Part: FUEL SYS — FLUCTUATES (LT ENGINE)

LT FUEL FLOW FLUCTUATION DURING CLIMB AND CRUISE FOLLOWED BY LT ENG FAILURE, FOLLOWED BY LT ENGINE VIBRATION.

Part: CONTROL CABLE — OUT OF RIG (AILERONS)

THE AIRCRAFT HAS AN AGGRESSIVE ROLL LEFT WITH THE ASSOCIATED TRIM TAB CENTERED. PLACED A YOKE LEVEL ON THE YOKES AND OPENED THE AFT CABIN FLOOR. INSERTED A RIG PIN IN THE AILERON SECTOR. PLACED THE AILERON TRIM TO NEUTRAL. FOUND THE RT AILERON ABOVE STREAM LINE OF WING AND TRIM TAB BELOW STREAMLINE OF AILERON. ADJUSTED THE RT AILERON WING CABLES TO STREAMLINE AILERON TO WING. LT AILERON CHECKS GOOD. TENSION AND TRAVEL CHECKS GOOD ON AILERONS. ADJUSTED TRIM TAB ACTUATOR TO STREAMLINE TRIM TAB TO AILERON. TRAVEL CHECKS GOOD. WITH YOKES LEVEL AND TRIM CENTERED. AILERONS AND TRIM TAB ARE STREAMLINED WITH THE WING. REMOVED RIG PIN. CLOSED AFT CABIN FLOOR IAW MM 27-11-00.

Part: VERTICAL GYRO — FAULTY (COCKPIT) · airframe 8,673 hrs · 7,141 cycles

AUTOPILOT MALFUNCTION - LEVEL AT 41000 MSL, THE AUTOPILOT AGGRESSIVELY PITCHED UP TO OVER 1000 FPM. THE AUTOPILOT WAS DISCONNECTED. AFTER 1 MINUTE, THE AUTOPILOT WAS RECONNECTED AND PROBLEM REOCURRED. REMOVED FAULTY LT SIDE PITOT STATIC PORT HOSE AND NR 1 VERTICAL GYRO (FAULTY) INSTALLED NEW HOSE AND REPAIRED VG. PERFORMED PITOT STATIC SYSTEM LEAK TEST GOOD. PERFORMED OPERATIONAL CHECK GOOD

Part: UNKNOWN — UNKNOWN (RT ENGINE) · airframe 8,489 hrs · 6,998 cycles

DESCENDING THROUGH 11,000 FT, RT ENGINE LOW FUEL PRESSURE ANNUNCIATOR ILLUMINATED, TRIGGERING RT FUEL BOOST ANNUNCIATOR TO ILLUMINATE. RAN THE ABNORMAL CHECKLIST AND LANDED. NO ENGINE FLUCTUATIONS OR OTHER ENGINE INDICATIONS WERE NOTED. [SUP 4-19-07] SUMPED RT WING TANKS. REMOVED ENGINE FUEL FILTER AND INSTALLED A NEW FILTER. INSTALLED COWL. REMOVED RT ENGINE FUEL LOW PRESSURE SWITCH AND INSTALLED A NEW SWITCH. ALL LEAK AND OPS CHECKS GOOD. ALL WORK DONE IAW CHAPTER 73-30-02 OF THE 560 MM.

Part: MASTER CYLINDER — MALFUNCTIONED (BRAKES) · airframe 8,385 hrs · 6,923 cycles

LT BRAKE ON RT SIDE TRAVELS ALMOST TO FLOOR DURING BRAKE APPLICATIONS. REMOVED CO-PILOTS IB AND OB BRAKE MASTER CYLINDERS AND INSTALLED NEW MASTER CYLINDERS IAW C560 MM 32-42-02. BLED BRAKES AS REQUIRED.

Part: COALESCER BAG — DIRTY (AFT SERVICE BAY) · airframe 8,263 hrs · 6,829 cycles

SHARP IRRITATING ODOR/SMELL MAINLY IN COCKPIT, STRONGER RIGHT AFTER TAKE OFF REMAINED THROUGH WHOLE FLIGHT INCREASED AGAIN DURING DESCENT. RAN ENGINES FOR 30 MINUTES AT 70% FOUND NO ODOR. CHECK OIL LEVELS GOOD. NO SIGN OF EXTERNAL OIL LEAKS. CHECK ACM OIL LEVEL FULL. NO FLUID IN ACM EPA CAN EXAMINED ACM FOR OIL LEAKS NONE FOUND. CHECKED BLEED AIR LINE GOING TO ACM NO SIGNS OF OIL FOUND. REPLACED COLISER SOCK WITH NEW. RAN ENGINES AT 80% FOR 15 MINUTES NO ODOR NOTICED. ENGINE OIL LEVELS STAYED CONSTENT IAW CE560 MM 21-70-00, 71-00-00, 21-21-06

Part: BRAKE — MALFUNCTIONED (MLG) · airframe 8,099 hrs · 6,692 cycles

RIGHT SEAT LEFT BRAKE REQUIRES MORE PRESSURE FOR RESPONSIVENESS COMPAIRED TO RIGHT SEAT RIGHT BRAKE. SERVICED AND BLED BRAKE SYSTEM IAW CESSNA 560 MM CH. 32-42-00

Part: HOSE — KINKED (BRAKE LINES) · airframe 8,079 hrs · 6,679 cycles

DURING TAXI WHEN MAKING A SHARP LEFT TURN, FULL DEFLECTION OF RUDDER PEDALS, F/O'S LEFT BRAKE PEDAL WOULD BECOME STIFF AND ROLL FORWARD, UPON STRAIGHTENING NOSE GEAR BRAKES RETURNED TO NORMAL, ONLY ON F/O SIDE, ONLY DURING LEFT TURN. M2B - T/S TO LOWER HOSE ON CO-PILOTS LT MASTER CYLINDER HITTING RUDDER TORQUE TUBE AND KINKING OVER STOPPING FLUID TO BRAKES. REMOVED & REPLACED LOWER HOSE AND REALIGNED FITTINGS FOR CLEARANCE OF TORQUE TUBE. INSP ALL MASTER CYL & HOSES FOR CLEARANCE AND CONDITION. ALL CHECKS GOOD. BLEED BRAKES C/W TAXI CHECKS. SYSTEM OP'S CHECKS SATISFACTORY AT THIS TIME. ALL WORK DONE IAW CE 560 M/M 32-40-00.

Part: BRAKE ASSY — MALFUNCTIONED · airframe 8,070 hrs · 6,670 cycles

WHEN LEFT RUDDER PEDAL IS PUSHED TO THE FLOOR AND THEN LT BRAKE IS APPLIED THERE IS NO PRESSURE AND TRAVELED TO THE FLOOR WITH NO BRAKING ACTION. BLED BRAKES AS PER CE560 AMM 32-42-00. BRAKE SYSTEM OPERATED NORMALLY DURING NORMAL BRAKING, AND WITH FULL RUDDER DEFLECTION TO LEFT & RIGHT SIDES. ALL MASTER CYLINDERS LEAK AND OP'S CHECK NORMALLY.

Part: BRAKE — LEAKING (LT MLG) · airframe 7,993 hrs · 6,605 cycles

DURING TAXI AIRCRAFT PULLS HARD TO RIGHT WHEN BRAKES ARE APPLIED; POST FLIGHT INSPECTION SHOWS SMALL FLUID LEAK ON FRONT SIDE OF LEFT BRAKE.

Part: BRAKE — CONTAMINATED (MLG) · airframe 7,856 hrs · 6,496 cycles

BRAKES VERY SOFT, YOU HAVE TO PUSH BRAKE PEDALS A LOT FURTHER THAN NORMAL TO MAKE BRAKES WORK IAW CESSNA 560 MM 32-42-00, PERFORMED BRAKE BLEEDING MAINTENANCE PROCEDURE. FOUND LARGE AMOUNTS OF AIR IN SYSTEM ALONG W/ LOW BRAKE FLUID LEVEL. REMOVED AIR AND REPLENISHED BRAKE FLUID DURING BRAKE BLEED PROCESS. OP'S CHECK GOOD, PEDALS TIGHT.

Part: FCU — FAILED · airframe 7,347 hrs · 6,087 cycles

DID NOT GET FULL PWR ON RIGHT HAND ENGINE DURING STATIC TAKEOFF, N1 75.9 ITT 450, N2 83 WITH THROTTLES FULL FWD. REMOVED AND REPLACED RIGHT ENGINE FCU AND FUEL PUMP. ENGINE OPERATES NORMAL AT THIS TIME IAW PWA M/M 71-00-00.

Part: BRAKE — MALFUNCTIONED (MLG) · airframe 1,636 hrs · 1,360 cycles

PILOTS LEFT BRAKE ALMOST GOES TO THE FLOOR. ITEM IS UNDER INVESTIGATION.

Part: TRANSDUCER — MALFUNCTIONED (ANTI SKID SYS) · airframe 7,298 hrs · 6,042 cycles

CAPT LEFT BRAKE PEDAL INTERMITTENTLY LOSES PRESSURE IN TURNS. REMOVED AND REPLACED LT ANTI SKID TRANSDUCER IAW CE 560 MM 32-42-07.

Part: BRAKE ASSY — WEAK (MLG) · airframe 7,249 hrs · 6,005 cycles

COPILOT'S BRAKE PEDALS ARE SOFT. ITEM IS UNDER INVESTIGATION.

Part: SKIN — CORRODED (WING)

UPON INSPECTION OF WING DEICE BOOTS, THE AERODYNAMIC FILLER WAS DETERMINED TO BE SEPARATING FROM SKIN CAUSING THE DEICE BOOT TO DEBOND. THE DEICE BOOT WAS REMOVED AND SKIN CLEANED OF DEFECTION FILLER. AT THIS TIME, THE SKIN WAS FOUND TO BE CORRODED AT THE LOWER INBOARD SECTION. LEFT WING CORROSION VARIED BETWEEN PITS .005 INCH AND .041 INCH DEEP RIGHT WING SKIN PITS RANGED FROM .002 INCH TO .008 INCHE DEEP. (X)

Part: SKIN — CORRODED (WING)

UPON INSPECTION OF WING DEICE BOOTS, THE AERODYNAMIC FILLER WAS DETERMINED TO BE SEPARATING FROM SKIN CAUSING THE DEICE BOOT TO DEBOND. THE DEICE BOOT WAS REMOVED AND SKIN CLEANED OF DEFECTION FILLER. AT THIS TIME, THE SKIN WAS FOUND TO BE CORRODED AT THE LOWER INBOARD SECTION. LEFT WING CORROSION VARIED BETWEEN PITS .005 INCH AND .041 INCH DEEP RIGHT WING SKIN PITS RANGED FROM .002 INCH TO .008 INCH DEEP. (X)

Part: NUT — MISSING (MLG)

WHILE INSPECTING LANDING GEAR ASSY DETERMINED BOTH MAIN LANDING GEAR SQUAT SWITCHES MISSING JAM NUT THAT SECURES THE ROD END TO THE TORQUE LINK. THE SQUAT SWITCH ASSY COULD BE TURNED AND MOVED.